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Master Thesis Report 3D Flow Simulation of the NASA Rotor 67 Plot of C.A. Outlet Plane Total Pressure versus Radial Span Position 1.8 C.A. Total Pressure for Radial Average Total P each R. ressure 1.6 1.4 1.2 1.0 0.8 0.6 0.4 0.2 0.0 4000 6000 8000 10000 16000 18000 12000 14000 Total Pressure [Pascal] Figure 7.11: Plot of Circumferential Averaged Total Pressure at various Spanwise Radial Position As seen in figure 7.11, the circumferential averaged total pressure reduces as we approach the tip of the spanwise radial position. This is expected since the fuselage boundary layer accumulates primarily at region close to the bottom segment of the outlet plane, leading to a greater pressure drop circumfer- entially. The non uniform boundary condition would then be applied onto the NASA Rotor 67 based on a scaling rule so as to fit the exact geometry of the blade. The radial averaged total pressure was then computed using the Riemann sum approach. The computed value of the radial averaged total pressure was found to be 12609.15 Pascal. The obtained results from figure 7.11 will be used as the non uniform inlet boundary condition while the uniform inflow condition will be based on the radial averaged total pressure. The outlet static pressure condition of the fan was then obtained by using the total to static pressure ratio found from [16]. With the inlet total pressure as well as the outlet static pressure quantified, the 3D simulations were performed. 7.3 ANSYS CFX Solver Settings and Mesh Convergence Studies In this section of the chapter, the simulation settings used in the ANSYS CFX solver will be explained. As the CFD solver SU2 was not able to simulate 3D geometries with periodic boundary condition despite extensive testing, ANSYS CFX was employed as a backup CFD solver for this part of the simulation. Other than ensuring a ’good’ mesh for a converged simulation, it is also necessary to have an optimal set of solver parameters for the simulation. The most commonly considered parameters used for the simulation will be described in this section. 79 Radial Position [m]PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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